GB1127826A - Gas turbine engine - Google Patents

Abstract

1,127,826. Gas turbine engine exhaust nozzles. ROLLS-ROYCE Ltd. June 9, 1967 [ June 17, 1966], No. 27150/66. Headings FIG, F1J and F1T. A gas turbine engine has a plurality of exhaust nozzles which are angularly spaced apart in an annular array, each exhaust nozzle being non- rigidly connected to casing structure of the engine by locating means, whereby the transmission of bending stresses from the casing structure to each exhaust nozzle is reduced. In the engine shown the turbine is indicated at 13 in Fig. 2, the assembly comprising an outer casing 14 and an inner casing 16, a further casing 15 being disposed around the outer casing 14. An exhaust cone 30 having a peripheral flange 31 is secured to the inner casing 16 by bolts 29, the peripheral flange 31 defining with the inner casing 16 a circumferential recess 33. A series of plate members 23 are secured by means of bolts 24 to the outer casing 14 and further casing 15, the plate members defining with the casing 14 a series of circumferential recesses 26. A series of exhaust nozzles 20 are mounted to receive the exhaust gases from the turbine 13, the nozzles being of generally elleptical form and having at their forward ends radially inner and radially outer flanges 22, 21, the flanges 22, 21, being. received within the circumferential recesses 33, 26, all respectively. Reeesses 45 in adjacent exhaust nozzles 20 co-operate to form a gap in which asbestos or other packing material 46 is received. Radially extending pipes 35 pass through openings in the downstream ends of the plate members 23, in the flanges 42 which are formed integrally with the peripheral flange 31, and in the exhaust cone 30, whereby air under pressure may be supplied to the interior of the exhaust cone for cooling purposes. Springs 34 are disposed between the downstream ends of the exhaust nozzles 20 for tranmission of loads therebetween.